Stagnation enthalpy effects on hypersonic turbulent compression corner flow at moderate Reynolds numbers

This work investigates the interaction of turbulent hypersonic flows with a 15^∘{} compression corner using direct numerical simulations. Different values of stagnation enthalpy, ranging approximately from 600kJ to 4MJ, are considered. Vibrational excitation of the gas molecules is also included in the model for the higher stagnation enthalpy cases. The analysis presented in the manuscript illustrates the effects of the flow thermodynamic state on quantities that determine the main mechanical and thermal stresses generated on a hypersonic vehicle, namely the shear stress, heat flux, and pressure fluctuations at the wall.